JPS6226329A - Control method of cooling air quantity - Google Patents
Control method of cooling air quantityInfo
- Publication number
- JPS6226329A JPS6226329A JP60165996A JP16599685A JPS6226329A JP S6226329 A JPS6226329 A JP S6226329A JP 60165996 A JP60165996 A JP 60165996A JP 16599685 A JP16599685 A JP 16599685A JP S6226329 A JPS6226329 A JP S6226329A
- Authority
- JP
- Japan
- Prior art keywords
- air
- gas turbine
- cooling
- temperature
- cooling air
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
- F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01P—COOLING OF MACHINES OR ENGINES IN GENERAL; COOLING OF INTERNAL-COMBUSTION ENGINES
- F01P7/00—Controlling of coolant flow
- F01P7/02—Controlling of coolant flow the coolant being cooling-air
- F01P7/026—Thermostatic control
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
- F05D2270/3013—Outlet pressure
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
Description
【発明の詳細な説明】
〔発明の利用分野〕
本発明は、ガスタービンを冷却用空気によって冷却する
場合、該ガスタービンの燃焼状態に応じて最適流量の冷
却用空気を供給するように制御する方法に関するもので
ある。[Detailed Description of the Invention] [Field of Application of the Invention] When a gas turbine is cooled by cooling air, the present invention controls the supply of cooling air at an optimum flow rate depending on the combustion state of the gas turbine. It is about the method.
ガスタービンの効率は、その燃焼温を高くすることによ
シ、飛躍的に向上することは周知の事実である。しかし
、燃焼温匿の上昇に伴い、材料の開発を同時に進行させ
、高温に耐えうる材料を使用することが燃焼温度の上昇
を可能ならしめる第一の条件となる。しかしながら、現
状技術では。It is a well-known fact that the efficiency of a gas turbine can be dramatically improved by increasing its combustion temperature. However, as the combustion temperature increases, the first condition for increasing the combustion temperature is to simultaneously advance the development of materials and use materials that can withstand high temperatures. However, with the current technology.
材料開発が頭打ち状態にあって画期的な向上は望めない
ので、材料を冷却することによって使用部材の温度を下
げてよう方法をとっている例が多い。Since material development has reached a plateau and no groundbreaking improvements can be expected, many methods are used to lower the temperature of the parts used by cooling the material.
第6図及び第7図に、ガスタービンノズルの空気冷却に
係る従来技術を示す。第6図は冷却空気系統図、第7図
はノズル付近の断面図である。FIG. 6 and FIG. 7 show a conventional technique related to air cooling of a gas turbine nozzle. FIG. 6 is a cooling air system diagram, and FIG. 7 is a sectional view of the vicinity of the nozzle.
タービンノズル13のメタル温度は現状最高レベルの材
料を使用しても800Cを越えて使用することは強度上
、寿命保証上の点から無理である。Even if the metal temperature of the turbine nozzle 13 is currently the highest level, it is impossible to use it at a temperature exceeding 800 C from the viewpoint of strength and life guarantee.
このため、ノズル13の温度はいかなる運転状態でも5
oot:’以下に押えておかねばならない。従って燃焼
器3を出る燃焼温度が800C以上のガスタービンでは
、空気圧縮機1の吐出空気4を利用してノズル13の内
面を冷却する必要がある。Therefore, the temperature of the nozzle 13 remains at 5
oot: 'Must be kept below. Therefore, in a gas turbine where the combustion temperature exiting the combustor 3 is 800 C or higher, it is necessary to cool the inner surface of the nozzle 13 using the discharge air 4 of the air compressor 1.
しかしながらこの冷却に用いる圧縮機吐出空気4の温度
は、通常のガスタービンでは350〜450Cの範囲に
あり、高温高圧タービンになるほどこの温度は高くなる
傾向にある。この冷却用空気をケーシング14から一旦
外に出し、インタークーラ6で水8と熱交換させること
によシ、冷却空気7の温Ifを200C前後まで下げる
手段が従来用いられており、この場合の冷却空気7のコ
ントロールは、温度センサー11によシ、制御器12に
て、温度200C程度の一定値に保持するよう、冷却水
8の量を弁9にて調整する方法がとられでいる。又、冷
却空気7の空気量はオリフィス10により一定値に押え
ている。However, the temperature of the compressor discharge air 4 used for this cooling is in the range of 350 to 450C in a normal gas turbine, and this temperature tends to increase as the temperature and pressure of the turbine increases. A conventional method has been used to lower the temperature If of the cooling air 7 to around 200C by letting this cooling air out of the casing 14 and exchanging heat with the water 8 in the intercooler 6. The cooling air 7 is controlled by a temperature sensor 11 and a controller 12 which adjusts the amount of cooling water 8 by a valve 9 so as to maintain the temperature at a constant value of about 200C. Further, the amount of cooling air 7 is kept at a constant value by an orifice 10.
一方、ガスタービンの出力と、燃焼温度15゜排気温度
16との関係は第8図に示す通シである。On the other hand, the relationship between the output of the gas turbine and the combustion temperature of 15 degrees and the exhaust temperature of 16 is as shown in FIG.
これは、大気温度一定の場合の関係であシ、この関係か
ら、燃焼温度15が1200tll’即ち、出力100
%の時の冷却空気量の必要量17を100チとした場合
、燃焼温度15が800Cの時は、冷却空気の供給は必
要なくなる。この関係を第9図に示す。これを出力割合
で表わしたものを第10図1819に示す。この場合、
オリフィス10及びノズル3の末端にて空気流量が絞ら
れている。オリフィス10のみで上記の空気流量をコン
トロールしている場合、吐出空気4の圧力が部分負荷に
なるに従い低下することから、第10図18に示す実線
18の如き実流空気量となる。従って、前記のオリフィ
ス10(第6図)の位置に、これに代る弁を設けて必要
空気量19と出力割合との関係に基づいて空気量7ft
調整することも可能である。This is the relationship when the atmospheric temperature is constant, and from this relationship, the combustion temperature 15 is 1200 tll', that is, the output 100
If the required amount 17 of the cooling air amount at the time of % is 100 inches, when the combustion temperature 15 is 800C, there is no need to supply cooling air. This relationship is shown in FIG. 1819 in FIG. 10 shows this expressed as an output ratio. in this case,
The air flow rate is restricted at the orifice 10 and the end of the nozzle 3. When the above-mentioned air flow rate is controlled only by the orifice 10, the pressure of the discharged air 4 decreases as the load becomes partial, so that the actual air flow rate becomes as shown by the solid line 18 shown in FIG. 10. Therefore, an alternative valve is provided at the position of the orifice 10 (FIG. 6), and the air amount is 7 ft based on the relationship between the required air amount 19 and the output ratio.
Adjustment is also possible.
しかしながら、ガスタービンは、運転時の大気温度によ
って吸込空気量が増減するため、ガスタービン内部の特
性が変る。However, since the intake air amount of a gas turbine increases or decreases depending on the atmospheric temperature during operation, the characteristics inside the gas turbine change.
第11図に、大気温度が変化した場合の燃焼温度15.
15 a、 15 bの関係を示す。とれから必要
空気量と出力の関係を第12図に示す。これよシ例えば
同じく50チの出力割合における必要空気流量は、大気
温度50Cで設計冷却空気量の60チ必要であり、15
Cで35%、−20Cでは、0チとなる。このため、先
に述べた出力割合による制御を実施した場合、制御設計
を15Cの曲線でインプットしておくと50%出力では
、冷却空気量が一20Cでは35チ余分に流すことにな
シ、効率向上の点から望ましくない。又、50Cの場合
は25チの冷却空気量が不足することになり、これは直
ちにノズルのメタル温度上昇につながシ、運転不可能の
事態を引き起こす虞れが有る。Fig. 11 shows the combustion temperature 15. when the atmospheric temperature changes.
The relationship between 15a and 15b is shown. Figure 12 shows the relationship between the amount of air required and the output. For example, the required air flow rate at an output ratio of 50 inches is 60 inches, which is the designed cooling air amount at an atmospheric temperature of 50C, and 15 inches.
It is 35% at C and 0 chi at -20C. For this reason, when implementing control based on the output ratio mentioned above, if the control design is input using a 15C curve, at 50% output, the amount of cooling air will be 120C, which means that an additional 35 cm will flow. This is undesirable from the standpoint of improving efficiency. In addition, in the case of 50C, the amount of cooling air of 25 inches will be insufficient, which will immediately lead to a rise in the temperature of the nozzle metal, and there is a possibility that it will become impossible to operate.
又、ガスタービンの効率向上策として、インレットガイ
ドベーンを出力により開閉することによって吸込空気i
t加減し、これにより部分負荷域まで燃焼温度最高の点
を保持し、部分負荷時の有効熱落差の有効利用と、排気
温度上昇によるボトムサイクルの効率向上を図る手段を
講じる場合がある。In addition, as a measure to improve the efficiency of gas turbines, the intake air i is
In some cases, measures are taken to maintain the maximum combustion temperature up to the partial load range by increasing or decreasing the combustion temperature, thereby making effective use of the effective heat drop during partial load and improving bottom cycle efficiency by raising the exhaust gas temperature.
このインレットガイドベーンコントロールをした場合の
燃焼温度15C1排気温度16Cの出力に対する関係を
第13図に示す。この関係より、出力に対する必要冷却
空気量を表わすと第14図19cとなる。即ち、第13
図燃焼源度15cが100%出力割合の点■と同一温度
である0点までは、同一量の冷却空気量が必要になるた
め、第14図必要冷却空気量19cは、■@θの折線と
なる。FIG. 13 shows the relationship between combustion temperature 15C1 exhaust temperature 16C and output when this inlet guide vane control is performed. From this relationship, the required amount of cooling air relative to the output is expressed as shown in FIG. 14, 19c. That is, the 13th
The same amount of cooling air is required up to point 0, where the combustion source degree 15c is the same temperature as the point ■ at which the output rate is 100%, so the required cooling air amount 19c in Figure 14 is the broken line of ■@θ. becomes.
一方、これに対し、実際に冷却空気7の流れの末端であ
るノズル13t−流れる実流量は、前記のインレットガ
イドベーンを絞ることにより、吐出空気4の圧力が下る
ため、第10図に示した実流空気量18よりも更に下シ
、線18aの如くなる。On the other hand, the actual flow rate through the nozzle 13t, which is the end of the flow of the cooling air 7, is as shown in FIG. The line 18a is further below the actual air flow rate 18.
この為、第14図O点において、実流空気量18aは、
必要空気量19Cにルして約101不足する。Therefore, at point O in Fig. 14, the actual flow air amount 18a is:
There is a shortage of about 101 points compared to the required air amount of 19C.
これは、ノズル13のメタル温度を当初の目標値である
800Cに下げるために必要な空気t 19Cを下回る
ことになるため、この時のメタル温度は8401:’と
なり、強度上及び寿命上1問題となる。This is lower than the air t19C required to lower the metal temperature of the nozzle 13 to the original target value of 800C, so the metal temperature at this time is 8401:', which is a problem in terms of strength and life. becomes.
寿命は、メタル温度5ooCの場合に比し、メタル温度
840Cの場合は約1/8となり、大幅な寿命縮少とな
る。The lifespan is approximately 1/8 when the metal temperature is 840C compared to when the metal temperature is 5ooC, resulting in a significant reduction in lifespan.
又、公知例(%開55−112826)としてタービン
排気温度のみに基づいて冷却空気量を制御する方式が見
られるが、この公知例の場合は、大気温度一定の場合を
想定しているもので下記のケースにおいて燃焼温度と排
気温度の関連性が崩れるため、正確な燃焼温度を把握す
ることができずに冷却空気量の過大、過少といった不具
合が生じる。In addition, there is a known example (% open 55-112826) that controls the amount of cooling air based only on the turbine exhaust temperature, but this known example assumes that the atmospheric temperature is constant. In the following cases, the relationship between the combustion temperature and the exhaust temperature breaks down, making it impossible to accurately determine the combustion temperature, resulting in problems such as excessive or insufficient amount of cooling air.
即ち。That is.
(1)大気温度変化による吸込空気量変化時に対応でき
ない。(1) Unable to respond to changes in intake air amount due to changes in atmospheric temperature.
(11)設計ミスマツチがあった場合、とれに対応して
適宜の制御をすることができない。(11) If there is a design mismatch, it is not possible to perform appropriate control in response to the mismatch.
OiD 経年変化によるガスバス汚れ、及び摩耗に対
応して適宜の制御をすることができない。OiD Appropriate control cannot be performed in response to gas bath contamination and wear caused by aging.
1iD 製作公差範囲内での形状変化に対応できない
。1iD Cannot handle shape changes within manufacturing tolerance range.
本発明は上述の事情に鑑みて為されたもので。 The present invention has been made in view of the above-mentioned circumstances.
その目的は冷却空気流it量制御て、ガスタービンのホ
ットガスパーツのメタル温度を適正に調節し得る方法を
提供するにある。The purpose is to provide a method for appropriately adjusting the metal temperature of hot gas parts of a gas turbine by controlling the amount of cooling air flow.
上記の目的を達成する為に創作した本発明の制御方法に
ついて、先ず、その基本的原理を略述する。First, the basic principle of the control method of the present invention created to achieve the above object will be briefly described.
従来技術においては、もっばらガスタービンの排気温度
のみに基づいてホットガスパーツの冷却側8t−行って
いたが、冷却制御のために基準とすべきは燃焼温度であ
って排気温度ではない。大気温度等の大気条件が一定で
あると仮定すれば上記の従来技術(排気温度基準の制御
)が成立し得るが、大気条件が一定でないという現実の
問題においては、燃焼温度を算出して、これに基づいて
冷却側1lKlを行わねばならない。In the prior art, the hot gas parts were cooled based solely on the exhaust gas temperature of the gas turbine, but the reference for cooling control is the combustion temperature, not the exhaust temperature. If it is assumed that atmospheric conditions such as atmospheric temperature are constant, the above conventional technology (control based on exhaust temperature) can be achieved, but in real problems where atmospheric conditions are not constant, combustion temperature is calculated, Based on this, the cooling side 11Kl must be carried out.
上に述べた原理に基づいて前記の目的(ホットガスパー
ツの適正な温度管理)f:達成するため。To achieve the above objective (appropriate temperature control of hot gas parts) f: based on the above-mentioned principle.
本発明の冷却空気量制御方法は、ガスタービンの排気温
度及び圧縮空気圧力を測定し、この測定値に基づいて燃
焼温度を算出して運転条件を判定し、この運転条件に適
合するように冷却空気tを制御することを特徴とする。The cooling air amount control method of the present invention measures the exhaust gas temperature and compressed air pressure of a gas turbine, calculates the combustion temperature based on the measured values, determines the operating conditions, and cools the gas turbine to suit the operating conditions. It is characterized by controlling air t.
次に、本発明の一実施例f:第1図について説明する。 Next, one embodiment f of the present invention: FIG. 1 will be described.
本図は本発明の制御方法を実施するために構成した制御
系統を付記したガスタービンの冷却系統図である。This figure is a cooling system diagram of a gas turbine with a control system configured to implement the control method of the present invention.
空気圧縮機1の吐出空気4の圧力を圧力計22にて測定
するとともにタービン2の排気温度を温度計23にて測
定する。この両者を流量演算機21にインプットする。The pressure of the air 4 discharged from the air compressor 1 is measured with a pressure gauge 22, and the exhaust gas temperature of the turbine 2 is measured with a thermometer 23. Both of these are input to the flow rate calculator 21.
この演算機21の中で、吐出圧力及び排気温度より冷却
空気必要流量を計算する。その関係は、ガスタービンの
一般的な特性として第2図に示すごとく、排気温度、吐
出圧力よシ燃焼温度が算出できるという関係を利用し。In this calculator 21, the required flow rate of cooling air is calculated from the discharge pressure and exhaust temperature. This relationship is based on the general characteristic of gas turbines, as shown in Figure 2, that the exhaust temperature, discharge pressure, and combustion temperature can be calculated.
これより燃焼温度に相当する冷却空気必要量f、算出す
るものである。即ち、第2図の排気温度、吐出圧力と燃
焼温度の関係より、第3図に示す排気温度、吐出圧力と
必要冷却空気量の関係を導き出し、この関係を演算機2
1にインプットしておく。From this, the required amount f of cooling air corresponding to the combustion temperature is calculated. That is, the relationship between exhaust temperature, discharge pressure, and required cooling air amount shown in FIG. 3 is derived from the relationship between exhaust temperature, discharge pressure, and combustion temperature shown in FIG.
Enter it in 1.
この演算機にて冷却空気必要量を算出し、この信号を空
気流量制御弁20に指令し、制御弁20にて冷却空気量
7をコントロールする。This calculator calculates the required amount of cooling air, and sends this signal to the air flow rate control valve 20, which controls the amount of cooling air 7.
又、冷却空気7の最大可能流量は、前述第14図の実流
空気量18aとなるがこれは、吐出空気4の圧力によっ
て次の式より定まる。Further, the maximum possible flow rate of the cooling air 7 is the actual flow rate 18a shown in FIG. 14, which is determined by the pressure of the discharge air 4 according to the following equation.
G=AXKX弄マ扉乃 ここで G:最大可能流量 λ:最少絞り部面積 に:係数 P:吐出空気4の圧力 ΔP:圧力差 T:空気温度 この関係を第4図に示す。G=AXKX Fuck Matoino Here, G: Maximum possible flow rate λ: Minimum drawing area to: coefficient P: Pressure of discharge air 4 ΔP: pressure difference T: Air temperature This relationship is shown in FIG.
この量大可能流量と、流量演算機21で算出した必要空
気流量とを比較し、必要空気流量が最大可能流量以下で
あれば、第5図に示すごとく、冷却空気温度を目標温度
200C一定に保持する。This large possible flow rate is compared with the required air flow rate calculated by the flow rate calculator 21, and if the required air flow rate is less than the maximum possible flow rate, the cooling air temperature is kept constant at the target temperature of 200C, as shown in Figure 5. Hold.
又、必要空気流量が最大可能流量よシも大であれば、冷
却空気温度を下げるべく冷却水8の流量を調整する。こ
の制御は、圧力計22で測定した圧力と、演算機21か
らの必要空気量とを温度演算機12aにインプットし、
更に、冷却空気7の温度を温度計11にて測定し、これ
も演算機12aにインプットすることによって、冷却水
調整弁9に与える信号を演算機12aにて算出し、実施
するものとする。以上のように制御することにより。Furthermore, if the required air flow rate is greater than the maximum possible flow rate, the flow rate of the cooling water 8 is adjusted to lower the cooling air temperature. This control inputs the pressure measured by the pressure gauge 22 and the required air amount from the calculator 21 to the temperature calculator 12a,
Furthermore, the temperature of the cooling air 7 is measured by the thermometer 11, and this is also input to the computer 12a, so that the signal to be given to the cooling water regulating valve 9 is calculated and executed by the computer 12a. By controlling as above.
大気温度変化時およびインレットガイドベーン制御方式
ガスタービン等のいかなる運転条件においても、燃焼温
度に相当する最少必要冷却空気条件が設定されるため、
冷却空気量を最低限に絞ることができ、効率向上が図れ
ると共に、タービンノズル等のホットガスパーツのメタ
ル温度を目標値に設定することができるため1部品の寿
命維持に大きく貢献する。The minimum required cooling air condition corresponding to the combustion temperature is set under any operating conditions such as when atmospheric temperature changes and inlet guide vane controlled gas turbines.
The amount of cooling air can be reduced to a minimum, improving efficiency, and the metal temperature of hot gas parts such as turbine nozzles can be set to a target value, which greatly contributes to maintaining the life of a single part.
以上に説明した実施例においては、次のような効果が確
認された。In the examples described above, the following effects were confirmed.
(1) 大気温度が変化した場合も、全ての運転範囲
において冷却空気消費量が最少となるようにコントロー
ルすることができ、しかもホットガスパーツのメタル温
度を管理基準内に抑えることができた。(1) Even when atmospheric temperature changes, cooling air consumption can be controlled to a minimum in all operating ranges, and the metal temperature of hot gas parts can be kept within control standards.
(li) インレットガイドベーンコントロール方式
材のガスタービンに本実施例の方法を適用すると、部分
負荷における燃焼温度が高い場合においても、その燃焼
温度に相当する冷却条件が確保でき、ホットガスパーツ
の寿命維持が可能となシ、本発明を実施しない場合に比
して8倍の寿命が確保できた。(li) If the method of this example is applied to a gas turbine using an inlet guide vane control type material, even if the combustion temperature is high at partial load, cooling conditions corresponding to the combustion temperature can be secured, and the hot gas parts will have a long lifespan. Since maintenance was possible, a lifespan eight times longer than that without implementing the present invention was ensured.
GiD 上に述べたように必要冷却空気量を最少限に
コントロールすることによシ、50%出力割合点におけ
るガスタービン効率’e 6.8 %向上できた。GiD As mentioned above, by controlling the required amount of cooling air to the minimum, the gas turbine efficiency'e at the 50% output ratio point could be improved by 6.8%.
以上詳述したように、本発明の方法によれば。 As detailed above, according to the method of the present invention.
冷却空気量を制御して、ガスタービンのホットガスパー
ツのメタル温度を適正に調節することができ、ガスター
ビンの熱効率を阻害することなく。By controlling the amount of cooling air, it is possible to appropriately adjust the metal temperature of the hot gas parts of the gas turbine, without impairing the thermal efficiency of the gas turbine.
耐久性、信頼性の向上に貢献するところ多大である。This greatly contributes to improved durability and reliability.
2g1図は本発明方法の一実施例におけるガスタービン
の冷却、制御系統図である。
第2図乃至第5図は上記実施例の効果を説明するための
図表である。
第6図及び第7図は従来の制御方法の説明図で第6図は
冷却、制御系統を示し、第7図はノズル付近の断面を示
している。
第8図乃至第14図はガスタービンの温度に関する問題
点を説明するための図表である。
1・・・圧縮機、2・・・タービン、3・・・燃焼器、
4・・・吐出空気、5・・・燃焼空気、6・・・インタ
ークーラ、7・・・冷却空気、8・・・冷却水、9・・
・冷却水制御弁、10・・・オリフィス、11・・・温
度計、12・・・温度演算機、13・・・ノズル、14
・・・タービンケーシング。
15・・・燃焼温度、16・・・排気温度、17・・・
必要空気量、18・・・実流空気量、19・・・必要空
気量。
20・・・流量制御弁、21・・・流量演算機、22・
・・圧力計、23・・・排気温度計。Figure 2g1 is a cooling and control system diagram of a gas turbine in one embodiment of the method of the present invention. FIGS. 2 to 5 are charts for explaining the effects of the above embodiment. 6 and 7 are explanatory diagrams of a conventional control method, with FIG. 6 showing a cooling and control system, and FIG. 7 showing a cross section near the nozzle. FIGS. 8 to 14 are charts for explaining problems related to the temperature of the gas turbine. 1...Compressor, 2...Turbine, 3...Combustor,
4...Discharge air, 5...Combustion air, 6...Intercooler, 7...Cooling air, 8...Cooling water, 9...
・Cooling water control valve, 10... Orifice, 11... Thermometer, 12... Temperature calculator, 13... Nozzle, 14
...Turbine casing. 15... Combustion temperature, 16... Exhaust temperature, 17...
Required air amount, 18...actual flow air amount, 19...required air amount. 20...Flow rate control valve, 21...Flow rate calculator, 22.
...Pressure gauge, 23...Exhaust temperature gauge.
Claims (1)
却する方法において、当該ガスタービンの排気温度およ
び圧縮空気圧力を測定し、上記の測定値に基づいて燃焼
温度を算出して運転条件を判定し、上記の運転条件に適
合するように前記の冷却用空気流量を制御することを特
徴とする冷却空気量制御方法。 2、前記の冷却用圧縮空気は、空気圧縮機の吐出空気を
一旦ガスタービン外に導き出し、流量調整弁によつて流
量を制御した後にガスタービンのノズル付近に供給する
ものであることを特徴とする特許請求の範囲第1項に記
載の冷却空気量制御方法。 3、前記のガスタービン外に導出した空気は、熱交換器
によつて冷却した後にガスタービンのノズル付近に供給
するものであることを特徴とする特許請求の範囲第1項
又は同第2項に記載の冷却空気量制御方法。[Claims] 1. In a method of cooling hot parts of a gas turbine with compressed air, the exhaust temperature and compressed air pressure of the gas turbine are measured, and the combustion temperature is calculated based on the measured values. A method for controlling the amount of cooling air, characterized in that the operating conditions are determined based on the operating conditions, and the cooling air flow rate is controlled to match the operating conditions. 2. The cooling compressed air is characterized in that the air discharged from the air compressor is once led out of the gas turbine, the flow rate is controlled by a flow rate regulating valve, and then the compressed air is supplied to the vicinity of the nozzle of the gas turbine. A cooling air amount control method according to claim 1. 3. The air led out of the gas turbine is supplied to the vicinity of the nozzle of the gas turbine after being cooled by a heat exchanger. The cooling air amount control method described in .
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP60165996A JPH0643811B2 (en) | 1985-07-29 | 1985-07-29 | Gas turbine hot parts cooling method |
US06/888,007 US4767259A (en) | 1985-07-29 | 1986-07-22 | Cooling air flow controlling apparatus for gas turbine |
FR8610830A FR2585407B1 (en) | 1985-07-29 | 1986-07-25 | DEVICE FOR CONTROLLING THE CIRCULATION OF THE COOLING AIR OF A GAS TURBINE |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP60165996A JPH0643811B2 (en) | 1985-07-29 | 1985-07-29 | Gas turbine hot parts cooling method |
Publications (2)
Publication Number | Publication Date |
---|---|
JPS6226329A true JPS6226329A (en) | 1987-02-04 |
JPH0643811B2 JPH0643811B2 (en) | 1994-06-08 |
Family
ID=15822931
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP60165996A Expired - Lifetime JPH0643811B2 (en) | 1985-07-29 | 1985-07-29 | Gas turbine hot parts cooling method |
Country Status (3)
Country | Link |
---|---|
US (1) | US4767259A (en) |
JP (1) | JPH0643811B2 (en) |
FR (1) | FR2585407B1 (en) |
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JPS6445926A (en) * | 1987-08-13 | 1989-02-20 | Toshiba Corp | Cooling method for gas turbine |
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JPS55112826A (en) * | 1979-02-21 | 1980-09-01 | Hitachi Ltd | Cooling system for gas turbine bucket |
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Cited By (12)
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JPS6445926A (en) * | 1987-08-13 | 1989-02-20 | Toshiba Corp | Cooling method for gas turbine |
JP2001207864A (en) * | 2000-01-25 | 2001-08-03 | General Electric Co <Ge> | Pressure modulating system and method of turbine side wall cavity |
JP2002181276A (en) * | 2000-09-27 | 2002-06-26 | General Electric Co <Ge> | Automatic draining orifice for pneumatic conduit line |
US7444819B2 (en) | 2003-09-30 | 2008-11-04 | Hitachi, Ltd. | Gas turbine installation including a compressed air humidifier and method |
JP2010261458A (en) * | 2009-05-08 | 2010-11-18 | General Electric Co <Ge> | Method related to control and operation of gas turbine |
JP2012082829A (en) * | 2010-10-06 | 2012-04-26 | Ansaldo Energia Spa | Control method for cooling turbine stage of gas turbine |
JP2013032758A (en) * | 2011-08-03 | 2013-02-14 | Mitsubishi Heavy Ind Ltd | Gas turbine control device and gas turbine control method |
JP2013092112A (en) * | 2011-10-26 | 2013-05-16 | Mitsubishi Heavy Ind Ltd | Gas turbine facility and method for controlling cooling air of the same |
JP2015512483A (en) * | 2012-03-23 | 2015-04-27 | アルストム テクノロジー リミテッドALSTOM Technology Ltd | Method for determining at least one combustion temperature for controlling a gas turbine, and gas turbine for performing the method |
WO2014050163A1 (en) * | 2012-09-27 | 2014-04-03 | 三菱重工業株式会社 | Method for controlling gas turbine cooling system, control device for executing this method, and gas turbine facility equipped with same |
JP2014070510A (en) * | 2012-09-27 | 2014-04-21 | Mitsubishi Heavy Ind Ltd | Control method for gas turbine cooling system, control device to execute the same and gas turbine facility mounted with the same |
US10465563B2 (en) | 2012-09-27 | 2019-11-05 | Mitsubishi Hitachi Power Systems, Ltd. | Method for controlling cooling system of gas turbine, control device performing the same, and gas turbine plant comprising the control device |
Also Published As
Publication number | Publication date |
---|---|
FR2585407A1 (en) | 1987-01-30 |
US4767259A (en) | 1988-08-30 |
JPH0643811B2 (en) | 1994-06-08 |
FR2585407B1 (en) | 1994-02-18 |
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